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Thursday, July 23, 2020 | History

3 edition of ALS liquid hydarogen turbopump found in the catalog.

ALS liquid hydarogen turbopump

ALS liquid hydarogen turbopump

summary final reprt

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  • 17 Currently reading

Published by Aerojet Propulsion Division, National Aeronautics and Space Administration, National Technical Information Service, distributor in Sacramento, CA, [Washington, DC, Springfield, Va .
Written in English

    Subjects:
  • Turbine pumps.,
  • Liquid hydrogen.,
  • Rocket engines.

  • Edition Notes

    Statementprepared by Deborah K. Rickman.
    Series[NASA contractor report] -- NASA CR-194646., NASA contractor report -- NASA CR-194646.
    ContributionsUnited States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14699563M

      An initial design of a split flow liquid hydrogen turbopump for the Dual Expander Aerospike Nozzle (DEAN) upper stage engine was completed. The engine nozzle is an annular aerospike. The engine cycle requires a combustion chamber pressure of 1, psia. The DEAN is designed to deli lbf of thrust and seconds of : John R. Black, Michael A. Arguello. A liquid-propellant rocket engine is a rocket propulsion system that uses a liquid propellant, combining a liquid fuel (such as kerosene or liquid hydrogen) in a thrust chamber with a liquid oxidizer (such as liquid oxygen or fuming nitric acid). Very efficient and controllable, such .

    hydrogen pump is a three-stage centrifugal pump while the high pressure liquid oxygen pump is a back- to-back single stage centrifugal pump with a single common volute. Unlike the SSME, the Ariane V has just one hydrogen and one oxygen pump as shown in Figure 1. Turbopump Rotor Dynamics Because of high power density and low damping in rocket turbopumps, these machines exhibit in their most extreme form a variety of vibration effects, which are either absent or masked by normal damping mechanisms in other turbo machines. The low damping is especially prominent in liquid hydrogen pumps, because of the.

    Acronyms and Abbreviations AL-LiAluminum-Lithium e. The USET hydrogen turbopump is roughly the size of a swimming pool pump and could drain the average-size swimming pool in 12 minutes, if water was to replace the liquid hydrogen fuel.


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ALS liquid hydarogen turbopump Download PDF EPUB FB2

The Liquid Hydrogen (LH2) Turbopump features a two-stage impeller pump with a pre-stage inducer driven by a two-stage turbine. The single shaft is supported by. Get this from a library. Liquid hydrogen turbopump ALS advanced development program. Vol. 1, Hot fire unit. [George C.

Marshall Space Flight Center.;]. Get this from a library. ALS liquid hydarogen turbopump: summary final reprt. [Deborah K Rickman; United States. National Aeronautics and Space Administration.]. NASA Technical Reports Server (NTRS) Liquid hydrogen turbopump ALS advanced development program.

Volume 1: Hot fire unit Item Preview. This report summarized analysis, design, and experimental work done on the liquid hydrogen turbopump for the ALS main : Deborah K. Rickman. Critical Speed Analysis of a 75 Ton Class Liquid Rocket Engine Turbopump due to Load Characteristics Journal of the Korean Society of Propulsion Engineers, Vol.

16, No. 4 Effects of flexible support stiffness on the nonlinear dynamic characteristics and stability of a turbopump. "The Development of Small Liquid Oxygen and Liquid Hydrogen Turbopumps of a LE-5 Rocket Engine", AIAA, f axis of turbopump.

The LH pump is installed in lower side of turbopump assembly and therefore its suction line forms a "U" letter TURBIN E GA GENERATO S R HEA EXCHANGE T R TURBIN E SPINNE R ALS liquid hydarogen turbopump book.

19 Hydraulic Diagram of. Full text of "NASA Technical Reports Server (NTRS) Liquid hydrogen turbopump ALS advanced development 1: Hot fire unit" See other formats enCdrp 30 90 31 f \ 5 ' Liquid Hydrogen Turbopump ALS Advanced Development Program Contract NAS Interface Control Document DR Volume I - Hot Fire Unit 8 October 1 Prepared For: National Aeronautics and.

The rotor of turbopump is directly supported by two sets of self-lubricated ball bearings in cryogenic pump fluid. The shaft seal of turbopump is installed between the cryogenic pump and the hot gas turbine.

The shaft seal system must seal the cryogenic propellants and the combustion gases (steam with rich hydrogen gas) safely and securely. The tribo characteristics of self-lubricating mm-bore ball bearings with a retainer of glass cloth-polytetrafluoroelhylene (PTFE) laminate, which has elliptical pockets with a large pocket clearance, were tested under thrust loads at speeds up to rpm, 2 million DN, in liquid hydrogen (LH 2) and in liquid nitrogen (LN 2).During testing, the bearing torque, outer-race temperature, and.

ALS liquid hydrogen turbopump: Advanced Development Program. By Nancy R. Shimp and George J. Claffy. Abstract. The point of departure (POD) turbopump concept was reviewed and finalized. The basis for the POD was the configuration presented in the Aerojet proposal.

After reviewing this proposal concept, several modifications were made. Authority-to-proceed (ATP) was given on 1 May APD was directed to close out the program on 6 August The objective of the program was to design and develop a highly reliable, low cost liquid hydrogen (LH2) turbopump for the ALS engine.

The total effort planned is defined in the Technical Implementation Plan, DR   American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Battery-Operated Liquid Transfer Pump Electric Automatic Siphon Pump Portable Liquid Transfer Pump for Fuel Gas Oil Gasoline Water, Hand Fuel Transfer Pump out of 5 stars 7 $ $.

The first, Test Cell A MW, featured an external device test pad, a highly shielded power and propellant flow control structure, a gaseous hydrogen-driven, MK IX liquid hydrogen turbopump (10, gpm, psi discharge pressure), ,gal liquid hydrogen tanks, and a gaseous hydrogen, nitrogen, and helium tank farm.

Liquid hydrogen turbopump ALS advanced development program. Volume 1: Hot fire unit. By Bruce Lindley. Abstract. The interface criteria for the Turbopump Test article (TPA) and the Component Test Facility located at NASA, Stennis Space Center is defined by this interface Control Document (ICD).

TPA ICD Volume 2 is submitted for the Cold Gas. D W Childs, D Klooster, H Borchard, et al. Transient lift-off test results for an experimental hybrid bearing in air, simulating a liquid hydrogen turbopump start transient.

ASME Turbomachinery Technical Conference and Exposition, Seoul, South Korea, GT ALS Turbomachinery Technology Advanced Development Programs are being pursued by Rocketdyne, Aerojet, and Pratt & Whitney to define and validate design approaches toward producing low-cost, reliable liquid-hydrogen and liquid-oxygen turbopumps for a kN ( klb) thrust Advanced Launch System.

A coupled analysis of inlet guide vanes, inducer blades, and the following struts is carried out via a Computational Fluid Dynamics (CFD) method.

The complex 3-D components are part of a liquid hydrogen fuel turbopump for Advanced Expander Test Bed (AETB) engine. Numerical simulation is. turbopump, placed in series for each of the liquid hydrogen and liquid oxygen loops, generated high pressures across a wide range of power levels.

A weight target of 2, kg (6, pounds) and tight Orbiter ascent envelope requirements yielded a compact design capable of generating a nominal chamber pressure of kg/cm 2(3, pounds/in 2. A turbopump is a propellant pump with two main components: a rotodynamic pump and a driving gas turbine, usually both mounted on the same shaft, or sometimes geared purpose of a turbopump is to produce a high-pressure fluid for feeding a combustion chamber or other use.

There are two types of turbopumps: a centrifugal pump, where the pumping is done by throwing fluid .Liquid hydrogen and liquid oxygen turbopump conceptual designs were prepared and the designs were used to establish hydrostatic bearing size and performance requirements.

The turbopump designs included provision for operation when bearing supply pressure is insufficient to support the rotor.The idea of liquid rocket as understood in the modern context first appears in the book The Exploration of Cosmic Space by Means of Reaction Devices, by the Russian school teacher Konstantin seminal treatise on astronautics was published in Maybut was not distributed outside Russia until years later, and Russian scientists paid little attention to it.